Proceedings of the Vertical Flight Society 78th Annual Forum最新文献_第7页

Helicopter Rotor Blade Planform Optimization Using Parametric Design and Multi-Objective Genetic Algorithm 基于参数化设计和多目标遗传算法的直升机旋翼平面优化

Proceedings of the Vertical Flight Society 78th Annual Forum Pub Date : 2022-05-10 DOI: 10.4050/f-0078-2022-17482

Y. Wenren, Joon W. Lim, Luke D. Allen, R. Haehnel, I. Dettwiller

{"title":"Helicopter Rotor Blade Planform Optimization Using Parametric Design and Multi-Objective Genetic Algorithm","authors":"Y. Wenren, Joon W. Lim, Luke D. Allen, R. Haehnel, I. Dettwiller","doi":"10.4050/f-0078-2022-17482","DOIUrl":"https://doi.org/10.4050/f-0078-2022-17482","url":null,"abstract":"\u0000 In this paper, an automated framework is presented to perform helicopter rotor blade planform optimization. This framework contains three elements, Dakota, ParBlade, and RCAS. These elements are integrated into an environment control tool, Galaxy Simulation Builder, which is used to carry out the optimization. The main objective of this work is to conduct rotor performance design optimizations for forward flight and hover. The blade design variables manipulated by ParBlade are twist, sweep, and anhedral. The multi-objective genetic algorithm method is used in this study to search for the optimum blade design; the optimization objective is to minimize the rotor power required. Following design parameter substitution, ParBlade generates the modified blade shape and updates the rotor blade properties in the RCAS script before running RCAS. After the RCAS simulations are complete, the desired performance metrics (objectives and constraints) are extracted and returned to the Dakota optimizer. Demonstrative optimization case studies were conducted using a UH-60A main rotor as the base case. Rotor power in hover and forward flight, at advance ratio = 0.3, are used as objective functions. The results of this study show improvement in rotor power of 6.13% and 8.52% in hover and an advance ratio of 0.3, respectively. This configuration also yields greater reductions in rotor power for high advance ratios, e.g., 12.42% reduction at advance ratio 0.4. \u0000","PeriodicalId":223727,"journal":{"name":"Proceedings of the Vertical Flight Society 78th Annual Forum","volume":"22 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-05-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124118932","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Flight Test of scaled MTEs for VTOL Certification using an Ultralight Coaxial Helicopter 使用一架超轻型同轴直升机进行缩放mte垂直起降认证的飞行测试

Proceedings of the Vertical Flight Society 78th Annual Forum Pub Date : 2022-05-10 DOI: 10.4050/f-0078-2022-17541

T. Jusko, Michael Jones, B. Grebing

引用次数: 0

Relative Adhesive Wear Performance of Rolling Element Bearings Material Pairs 滚动轴承材料副的相对黏着磨损性能

Proceedings of the Vertical Flight Society 78th Annual Forum Pub Date : 2022-05-10 DOI: 10.4050/f-0078-2022-17602

Robert L. Sadinski, Carl Hager(Jr.), David Prock

引用次数: 0

H145 New Comfort Experience: Upgrading From Four-Bladed HMR To Five-Bladed BMR H145全新舒适体验:从四刃HMR升级到五刃BMR

Proceedings of the Vertical Flight Society 78th Annual Forum Pub Date : 2022-05-10 DOI: 10.4050/f-0078-2022-17517

R. Rammer, M. Priems, S. Dreher, O. Dieterich

引用次数: 0

Rotorcraft Digital Twin: Exploiting On-board Data for Enhancing Sustainment and Operational Availability 旋翼机数字孪生:利用机载数据增强维护和操作可用性

Proceedings of the Vertical Flight Society 78th Annual Forum Pub Date : 2022-05-10 DOI: 10.4050/f-0078-2022-17600

Matt Harrigan, A. Sarlashkar, Raymond Beale(Jr.), Jared Kloda, Mark Kruse, Dennis Vanill

{"title":"Rotorcraft Digital Twin: Exploiting On-board Data for Enhancing Sustainment and Operational Availability","authors":"Matt Harrigan, A. Sarlashkar, Raymond Beale(Jr.), Jared Kloda, Mark Kruse, Dennis Vanill","doi":"10.4050/f-0078-2022-17600","DOIUrl":"https://doi.org/10.4050/f-0078-2022-17600","url":null,"abstract":"\u0000 Rotorcraft Digital Twin (RDT) is a Digital Transformation initiative to leverage on-board flight data, design data, maintenance records, and advanced analytical models to enhance the current sustainment paradigm, increase availability, reduce life-cycle cost, and to enable optimization of future designs. Many core capabilities have been integrated into RDT, such as load estimation, advanced regime recognition, gross weight estimation, fatigue damage accrual calculations, among others, which leverage a rich body of prior work. Multiple algorithms enable component life extensions, predictive maintenance, selection of the optimal set of assets for a particular mission or deployment to minimize the likelihood of unscheduled maintenance, supporting the Rotorcraft Structural Integrity Program (RSIP) requirements, and feeding field data back into the design process for continuous product improvements. A robust, generic, and reusable suite of algorithms and associated framework has been developed utilizing a common data model where possible. RDT has been developed with a modern cloud-native microservice software architecture which glues together carefully selected Free and Open-Source Software (FOSS) components.\u0000","PeriodicalId":223727,"journal":{"name":"Proceedings of the Vertical Flight Society 78th Annual Forum","volume":"75 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-05-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130713829","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Analysis of Rotor Noise during Maneuvering Flight based on COLRNS Solver 基于collns求解器的机动飞行旋翼噪声分析

Proceedings of the Vertical Flight Society 78th Annual Forum Pub Date : 2022-05-10 DOI: 10.4050/f-0078-2022-17439

Xi Chen, Weiqi Wang, Qi-jun Zhao, Muyang Lin

引用次数: 0

Time-Frequency Analysis of Experimental and Analytical Hub Loads of a Rotor Undergoing a Rotor Speed Change 转子转速变化时轮毂试验载荷和分析载荷时频分析

Proceedings of the Vertical Flight Society 78th Annual Forum Pub Date : 2022-05-10 DOI: 10.4050/f-0078-2022-17526

M. Sekula, C. Russell

{"title":"Time-Frequency Analysis of Experimental and Analytical Hub Loads of a Rotor Undergoing a Rotor Speed Change","authors":"M. Sekula, C. Russell","doi":"10.4050/f-0078-2022-17526","DOIUrl":"https://doi.org/10.4050/f-0078-2022-17526","url":null,"abstract":"\u0000 A two-part analytical study was conducted examining a small-scale, two-bladed rotor undergoing a change in rotor speed. First, a parametric study was conducted to understand how rotor transient response, determined using a time-marching solution, is affected by the choice of rotor wake model, blade elasticity, and inclusion of an elastic support structure model. The second part of the study compared results from an analytical model of the NASA Multirotor Test Bed (MTB) undergoing a rotor speed change to wind tunnel data. Since the analytical and experimental time histories were nonstationary signals, a Stockwell transform was employed to analyze the data in lieu of traditional Fourier transform-based methods. The analysis included extraction of time-varying frequency content of the rotor thrust and hub motion, damping ratios, instantaneous rotor speed, and instantaneous phase difference between thrust and hub motion. Use of a free wake model was found to be necessary to predict higher-harmonic thrust, however, it underpredicted the amplitude of the unsteady loads. Modeling the elasticity of the stiff rotor blades installed on the MTB resulted in minimal impact on the computed vibratory loads compared to a rigid blade model. The current analytical model of the MTB, including an elastic support structure, properly predicted the measured trends in the frequency content of the thrust.\u0000","PeriodicalId":223727,"journal":{"name":"Proceedings of the Vertical Flight Society 78th Annual Forum","volume":"28 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-05-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"128743124","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Blade Shape Optimization of Mars Helicopter Exploring Pit Craters 火星直升机探测坑坑的叶片形状优化

Proceedings of the Vertical Flight Society 78th Annual Forum Pub Date : 2022-05-10 DOI: 10.4050/f-0078-2022-17445

M. Sugiura, Masahiro Kanazaki, M. Sato, Takuma Minajima, Keita Kimura, A. Oyama, H. Sugawara, Y. Tanabe, Yuki Kishi, Daisuke Kikuchi, Kota Yoshikawa, Yuta Buto

{"title":"Blade Shape Optimization of Mars Helicopter Exploring Pit Craters","authors":"M. Sugiura, Masahiro Kanazaki, M. Sato, Takuma Minajima, Keita Kimura, A. Oyama, H. Sugawara, Y. Tanabe, Yuki Kishi, Daisuke Kikuchi, Kota Yoshikawa, Yuta Buto","doi":"10.4050/f-0078-2022-17445","DOIUrl":"https://doi.org/10.4050/f-0078-2022-17445","url":null,"abstract":"\u0000 Pit craters on Mars are assumed to be used as manned exploration bases and it is highly possible that life signature would be discovered there since its temperature is appropriate and it is less affected by radiation. Regarding pit crater exploration, helicopter which can climb and descend quickly is expected to be utilized. This paper introduces blade shape optimization of Mars helicopter exploring pit craters. Definition of a mission, selection of aircraft types, conceptual design, optimization of blade twist angle and airfoil, and rotor test are conducted. As a result, hexa-rotor which has robustness, resistance to gust, and fault tolerance is proposed. Moreover, it is confirmed that the mission can be accomplished, carrying instruments on the helicopter within payload weight. Hovering performance of the helicopter is improved by optimizing blade twisting angle and airfoil. And it is found that there is a good correlation between experiment and numerical simulation with respect to the helicopter's hovering performance. \u0000","PeriodicalId":223727,"journal":{"name":"Proceedings of the Vertical Flight Society 78th Annual Forum","volume":"30 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-05-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126744486","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

The Effect of Blade Tip Sweep Angle on Forward Flight Performance of a High-speed Helicopter 桨尖掠角对高速直升机前飞性能的影响

Proceedings of the Vertical Flight Society 78th Annual Forum Pub Date : 2022-05-10 DOI: 10.4050/f-0078-2022-17480

K. Kimura, Y. Tanabe, M. Sugiura

引用次数: 1

NGCTR-TD Tiltrotor Autorotation Numerical Investigation ngtr - td倾转旋翼自旋数值研究

Proceedings of the Vertical Flight Society 78th Annual Forum Pub Date : 2022-05-10 DOI: 10.4050/f-0078-2022-17551

F. Riccardi, Federico DelGrande, Giuliano Prando, Valentina Giuliani, M. Pecoraro, A. Ragazzi

{"title":"NGCTR-TD Tiltrotor Autorotation Numerical Investigation","authors":"F. Riccardi, Federico DelGrande, Giuliano Prando, Valentina Giuliani, M. Pecoraro, A. Ragazzi","doi":"10.4050/f-0078-2022-17551","DOIUrl":"https://doi.org/10.4050/f-0078-2022-17551","url":null,"abstract":"\u0000 Within the Clean Sky 2 Fast Rotorcraft platform, a Next Generation Civil Tilt-Rotor Technology Demonstrator (NGCTR-TD) is under development. The design phase has been successfully completed and first flight phase is planned within 2023. As part of design verification, the capability to perform a safe landing procedure after losing all engines power is investigated, with dedicated analysis planned in order to improve the transport category performance requirements, as verified for Legacy tilt-rotor platform. Such procedure consists in 4 different steps when starting from AP mode, and the analysis are focused on VTOL steady autorotation phase, being the one where tilt-rotor configuration shows higher peculiarity with respect to helicopter configuration, due to the presence of lifting surfaces. As first, preliminary considerations from helicopter theory are cited, and tilt-rotor peculiarities listed. Then, adopting the developed FlightLab numerical model, different solutions are investigated, starting from characterization in airspeed for a baseline configuration. Different sensitivity analyses are conducted to map the major effect for the specific topic, and best trade-off autorotation configuration/control strategy is obtained for NGCTR-TD. Such solution is investigated in the complete Weight/CG envelope to ensure control strategy robustness.\u0000","PeriodicalId":223727,"journal":{"name":"Proceedings of the Vertical Flight Society 78th Annual Forum","volume":"32 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-05-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114164654","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0